Turbine blade tip shroud

ABSTRACT

A turbine blade tip shroud ( 22 C,  22 D) with a seal rail ( 32 C,  32 D) oriented in a circumferential direction of rotation ( 29 ) relative to a turbine axis, and extending radially outward from the tip relative to the turbine axis. A first tooth ( 48, 68 ) and a second tooth ( 50, 70 ) form respective downstream and upstream lateral departures or bumps on the seal rail. Each tooth has a sharp top leading edge ( 48, 50, 68, 70 ) and a smoothly curved side surface ( 49, 51, 69, 71 ). A back portion ( 56, 76 ) of the seal rail may span linearly from a lateral peak ( 66, 78 ) of the second tooth to a back end ( 62 ) of the seal rail that is centered on an extended centerline ( 60 ) of a front portion ( 54, 74 ) of the seal rail. The teeth may be disposed proximate or over a stacking axis ( 52 ) of the blade.

This application is the US National Stage of International ApplicationNo. PCT/US2014/038700 filed May 20, 2014, and claims the benefitthereof. The International Application claims benefit of the 21 May 2013filing date of U.S. provisional patent application No. 61/825,601. Allapplications are incorporated by reference herein.

FIELD OF THE INVENTION

The invention relates to gas turbine blade tip shrouds and particularlyto a seal rail and cutter tooth configuration for a tip shroud.

BACKGROUND OF THE INVENTION

A gas turbine blade has a tip that closely brushes a surrounding shroud.The shroud channels the working gas flow through circular arrays ofblades. Each circular array is called a turbine stage, the first stagebeing just after the combustion section. The inner lining of the shroudis made abradable so that the blade tips can cut a path in it tominimize the blade tip-to-shroud clearance. This minimizes leakage ofthe working gas from the pressure side to the suction side of eachblade. Some blade designs include a tip shroud as shown in FIG. 1, whichis a plate on the blade tip. A seal rail may extend radially outwardfrom the plate. The rail is aligned circumferentially along the rotationdirection. It cuts a narrow groove in the shroud lining for working gassealing. The rail may include wider portions called teeth that cut thegroove wider than the rail to allow for proper blade to shroudclearances for tolerances and rotor axial movement.

A disadvantage of adding a tip shroud and seal rail to a blade design isadded weight. Cantilevered portions of the tip shroud must be rigid toresist flexing from centrifugal force. This limits possible weightreductions.

BRIEF DESCRIPTION OF THE DRAWINGS

The invention is explained in the following description in view of thedrawings that show:

FIG. 1 is a perspective view of a prior art turbine blade with a tipshroud.

FIG. 2 is a top view of a prior art tip shroud and seal rail.

FIG. 3 is a sectional view taken on line 3-3 of FIG. 2.

FIG. 4 is a top view of two adjacent tip shrouds showing aspects of anembodiment of the invention.

FIG. 5 is a sectional view taken on line 5-5 of FIG. 4.

FIG. 6 is a top view of a tip shroud showing aspects of a secondembodiment of the invention.

DETAILED DESCRIPTION OF THE INVENTION

FIG. 1 shows a prior art turbine blade 20A with a tip shroud 22A. Theblade has a root 23, a platform 24, and an airfoil 25 with a leadingedge 26 and a trailing edge 27. A transverse profile 30M of the airfoilmidsection is shown with a pressure side P and a suction side S. Anaxial direction 28 of the working gas flow and a circumferentialdirection 29 of blade rotation are shown. “Axial” means parallel to theturbine rotation axis. The circumferentially oriented seal rail 32A haswider portions or teeth 34, 35 for cutting a groove in the shroud liner.

FIG. 2 is a top view of a prior art turbine blade 20B showing a tipshroud 22B, a platform 24, and an airfoil 25 with a leading edge 26 anda trailing edge 27. A transverse profile 30T of the airfoil tip is shownwith a dashed line. An axial direction 28 of the working gas flow and acircumferential direction 29 of blade rotation are shown. Acircumferentially oriented seal rail 32B has first and second teeth 38,39 for cutting a groove in the shroud liner. Cooling air outlets 40 passthrough the tip shroud from cooling chambers in the airfoil 25. The railand teeth have fillets 42.

FIG. 3 is a sectional view taken on line 3-3 of FIG. 2, showing anabradable shroud liner 44 with a groove 46 therein that is cut by theteeth 38, 39. Abradable shroud liners are made of ceramic that may beporous and/or may have a honeycomb structure to increase abradability.Gas leakage over the blade tip is impeded by the top of the seal rail32B closely clearing the top of the groove 46.

FIG. 4 is a top view of two adjacent tip shrouds 22C, 23C showingaspects of an embodiment of the invention. An axial direction 28 of theworking gas flow and a circumferential direction 29 of blade rotationare shown. A circumferentially oriented seal rail 32C has first andsecond teeth 48, 50 for cutting a groove in the shroud liner. The firsttooth 48 or both teeth may be proximate or over a stacking axis 52 ofthe blade. The stacking axis is a radial line from the turbine axisthrough the center of mass of the blade. Proximity of the teeth to thestacking axis minimizes bending moment on the blade about the stackingaxis. Cooling air outlets 40 may pass through the tip shroud fromcooling chambers in the blade via the blade tip 30T. The rail and teethmay have fillets 42.

The teeth 48, 50 may be smoothly rounded or bumps extending upstream anddownstream from the seal rail 32C. The top leading edge of each tooth(the edge touched by lead lines 48, 50) may be sharp, with an includedangle B (FIG. 5) such as 90 to 100 degrees when viewed in section, whilethe side surfaces 49, 51 may be smoothly rounded. This combinationproduces clean cutting by the sharp edges plus smoothing of the sides ofthe groove 46 (FIG. 5) by the rounded sides of the teeth. The sides 49,51 can fly on the boundary layer of gas on the sides of the groove insome conditions, minimizing resistance. Such an air bearing effect ismaximized by the tooth sides being smooth and rounded. Only one tooth48, 50 is needed on each side of the rail 32C.

The rail 32C may have front and back portions 54, 56 with respect to therotation direction 29. The front portion 54 of the rail is ahead of theteeth 48, 50. It may be aligned with the rotation direction 29 as shownby centerline 58. The back portion 56 of the rail is behind the teeth.It may be angled back to the extended front centerline 58 as shown sothat the back end 62 of the rail aligns with the front end 64 of therail on the following tip shroud 23C. The back portion 56 of the railmay span linearly from the peak 66 or maximum lateral extent of the backtooth 50 to the back end of the rail 62 centered on the extendedcenterline 58. This configuration minimizes mass in the back portion 56of the rail for a given width thereof, since the shortest distancebetween two points is a straight line. The angle A between centerlines58, 60 of the front and back portions of the rail may be in a range suchas 2 to 3 degrees.

The tip shroud and seal rail as shown in FIG. 4 may be used in originalturbine manufacture or on replacement blades, which are also calledbuckets. This provides reduced mass and friction over the prior art ofFIG. 2.

FIG. 5 is a sectional view taken on line 5-5 of FIG. 4, showing anabradable shroud liner 44 with a groove 46 cut therein by the teeth 48,50 of FIG. 4.

FIG. 6 is a top view of a tip shroud 22D with aspects of a secondembodiment of the invention. An axial direction 28 of the working gasflow and a circumferential direction 29 of blade rotation are shown. Acircumferentially oriented seal rail 32D has first and second teeth 68,70 for cutting a groove in the shroud liner. The first tooth 68 or bothteeth may be proximate or over the stacking axis 52 of the blade. Therail and teeth may have fillets 42.

The teeth 68, 70 may be formed by smoothly rounded lateral departures orbumps on the seal rail 32D as shown. The top leading edge of each tooth(the edge touched by lead lines 68, 70) may be sharp, while the sides69, 71 may be smoothly rounded. Only one tooth 68, 70 is needed on eachside of the rail 32D.

The rail 32D may have front and back portions 74, 76 with respect to therotation direction 29. The front portion 74 is ahead of the teeth 68,70, and may be aligned with the rotation direction 29. The back portion76 is behind the teeth. It may span linearly from the peak 78 or maximumlateral extent of the back tooth 70 to a back end 62 of the seal railthat is centered on an extended centerline 60 of the front portion 72 ofthe rail. This configuration minimizes mass in the back portion 76 ofthe rail for a given width thereof, since the shortest distance betweentwo points is a straight line. The front and back portions 74, 76 of therail may have a common uniform thickness, although this is not arequirement.

The tip shroud and seal rail as shown in FIG. 6 may be used in originalturbine manufacture or on replacement blades, which are also calledbuckets.

The teeth pairs 48/50, 68/70 may be formed in a comma shape as viewedfrom above (FIGS. 4 and 6). This forms a smooth transition and allows amore constant rail thickness than in prior art (FIG. 2), resulting inmore uniform cooling and thermal expansion of the rail.

While various embodiments of the present invention have been shown anddescribed herein, it will be obvious that such embodiments are providedby way of example only. Numerous variations, changes and substitutionsmay be made without departing from the invention herein. Accordingly, itis intended that the invention be limited only by the spirit and scopeof the appended claims.

The invention claimed is:
 1. A turbine blade tip shroud, comprising aseal rail oriented in a circumferential direction of rotation relativeto a turbine axis, and extending radially outward from a shroud relativeto the turbine axis; and a first tooth and a second tooth extendingrespectively downstream and upstream from the seal rail with respect toa working gas flow, each tooth comprising a sharp top leading edge and asmoothly curved side surface; wherein a back portion of the seal railspans linearly from an upstream peak of the second tooth to a back endof the seal rail that is centered on an extended centerline of a frontportion of the seal rail.
 2. The turbine blade tip shroud of claim 1,wherein the back portion of the seal rail forms an angle of 2 to 3degrees relative to the extended centerline of the front portion of theseal rail.
 3. The turbine blade tip shroud of claim 1, wherein the sharptop leading edge of each tooth comprises an included angle of 90 to 100degrees between a top surface of the tooth and the side surface thereofas seen in section.
 4. The turbine blade tip shroud of claim 1, whereinthe first tooth is proximate a radius of the turbine axis that passesthrough a center of mass of the blade.
 5. A turbine blade tip shroud,comprising: a plate on a tip of a turbine blade; a seal rail oriented ina circumferential direction of rotation relative to a turbine axis, theseal rail extending radially outward from the plate relative to theturbine axis; a first tooth forming a lateral bump on a downstream sideof the seal rail with respect to a working gas flow, the first toothcomprising a sharp top leading edge; a second tooth forming a lateralbump on an upstream side of the seal rail with respect to the workinggas flow, the second tooth comprising a sharp top leading edge; the sealrail comprising a front portion ahead of the first tooth with respect tothe direction of rotation and a back portion behind the second toothwith respect to the direction of rotation, wherein the back portion ofthe seal rail spans linearly from a lateral peak of the second tooth toa back end of the seal rail that is centered on an extended centerlineof the front portion of the seal rail.
 6. The turbine blade tip shroudof claim 5, wherein the back portion of the seal rail forms an includedangle of 2 to 3 degrees with the extended centerline of the frontportion of the seal rail.
 7. The turbine blade tip shroud of claim 5,wherein each of the teeth has a smoothly curved side surface.
 8. Theturbine blade tip shroud of claim 5, wherein the sharp top leading edgeof each tooth comprises an included angle of 90 to 100 degrees between atop surface of the tooth and a side surface thereof as seen in section.9. The turbine blade tip shroud of claim 5, wherein the teeth areproximate or over a radius of the turbine axis that passes through acenter of mass of the blade.
 10. A turbine blade tip shroud, comprisinga seal rail oriented in a circumferential direction of rotation relativeto a turbine axis, and extending radially outward from the shroudrelative to the turbine axis; and a first tooth and a second toothextending from the seal rail respectively downstream and upstream withrespect to a working gas flow, the first and second teeth forming acontinuously smooth comma-shaped transition between a front portion ofthe seal rail and a back portion thereof as viewed from above; whereinthe back portion of the seal rail spans linearly from an upstream peakof the second tooth to a back end of the seal rail that is centered onan extended centerline of the front portion of the seal rail.